CN111577496A - Oil pump assembly suitable for piston type aircraft engine and piston type aircraft engine - Google Patents

Abstract

The invention discloses an oil pump assembly suitable for a piston type aero-engine, which comprises a first low-pressure oil pump, a second low-pressure oil pump, a box body, a first one-way valve connected with an oil outlet of the first low-pressure oil pump, a second one-way valve connected with an oil outlet of the second low-pressure oil pump, a fuel pressure accumulating oil rail connected with the first one-way valve and the second one-way valve, a fuel pressure sensor arranged on the fuel pressure accumulating oil rail and a pressure regulating valve connected with an oil outlet of the fuel pressure accumulating oil rail, wherein the first low-pressure oil pump, the second low-pressure oil pump, the first one-way valve, the second one-way valve and the pressure regulating valve are arranged in the box body. The invention is suitable for the oil pump assembly of the piston type aircraft engine, can reduce the complexity of the system and has high integration level. The invention also provides a piston type aero-engine.

Description

Oil pump assembly suitable for piston type aircraft engine and piston type aircraft engine

Technical Field

The invention belongs to the technical field of engines, and particularly relates to an oil pump assembly suitable for a piston type aircraft engine and the piston type aircraft engine.

Background

Piston type aircraft engines are widely applied to fixed-wing and rotor-wing aircrafts and are widely applied in the fields of civil and military unmanned planes and navigation aircrafts; the piston aeroengine is developed through the stages of a carburetor type gasoline engine and a mechanical pump type diesel engine, is developed to the aspects of an electric control gasoline engine, an electric control common rail type diesel oil and a heavy oil engine gradually at present, and is used as a common rail diesel engine, and the problem of ensuring the safety of a low-pressure oil way system is a key research subject.

In the field of aviation, a design scheme of key part redundancy is adopted as one of important means for guaranteeing the safety of a system, a scheme such as FADEC dual-channel system control, key sensor and actuator redundancy design and the like on a common rail diesel engine is mature in application, a dual low-pressure oil pump is adopted as an oil supply system design of the common rail diesel engine, and necessary monitoring measures are designed to guarantee sufficient safety, so that the design scheme is an important means for guaranteeing the robustness of a fuel system.

The design of the dual low-pressure oil pump of the engine faces the following obvious risk points:

1. the system complexity is high: on the premise of meeting the requirements of overall performance, reliability and the like of the engine, the system is designed to be as simple as possible. The higher system complexity brings more potential failure risk points, while also not being conducive to achieving engine lightweight design and power-to-weight ratio goals. The electric control gasoline engine is difficult to realize closed-loop control and adjustment of oil inlet quantity and oil spraying quantity of an oil sprayer, and is difficult to complete closed-loop timely adjustment of oil spraying quantity of a system under the condition that the oil delivery quantity of a low-pressure oil pump fluctuates greatly. The electric control gasoline engine usually adopts a mode of serially connecting double low-pressure oil pumps, the output flow difference is not large when the serially connected oil pumps work in double pumps and the single pump works, and the working requirement of the gasoline engine can be well met. The series low-pressure oil pump can be transplanted and applied to a common rail diesel engine in principle, but under the condition that a series low-pressure oil pump system needs to design a bypass to ensure that a single low-pressure oil pump is damaged, fuel can enter an oil inlet of the high-pressure oil pump through the bypass, the bypass must be provided with a check valve to ensure that the fuel cannot flow back to an oil tank and the single pump stops working, the other oil pump can suck or transfer oil through the check valve of the bypass, and the check valve must have enough small opening pressure and small pressure loss to ensure that the low-pressure oil pump close to the oil tank is damaged, the other low-pressure oil pump in series can suck the check valve open to lead the oil from the bypass, the overall complexity of the system is high, the check valve is blocked and fails due to blockage, leakage and aging of the bypass, and the like bring new risk points to the low-pressure oil circuit, so the series low-pressure oil pump, the system has high complexity and large potential risk points, and is not a good selection scheme of the common rail diesel engine;

2. system consistency is difficult to control: the difference of parameters such as fuel pressure, temperature and the like at the inlet ends of high-pressure oil pumps of different engines can be caused due to different lengths, bending degrees and along-process losses of connecting pipelines at different relative positions of the double low-pressure oil pumps, the pressure regulating valve and the sensor in a low-pressure fuel oil system, the difference can change oil inlet parameters for calibrating and curing the engines to influence the consistency of the whole system of the engines, so that parts in the system are scattered and arranged, and the risk of difficulty in controlling the consistency of the system is a problem which is difficult to solve at present;

3. fault alarm strategies lack a simple and effective solution.

Disclosure of Invention

The present invention is directed to solving at least one of the problems of the prior art. Therefore, the invention provides an oil pump assembly suitable for a piston type aircraft engine, and aims to reduce the complexity of the system.

In order to achieve the purpose, the invention adopts the technical scheme that: oil pump assembly suitable for piston aeroengine, including first low-pressure oil pump, second low-pressure oil pump, box, with first check valve that the oil-out of first low-pressure oil pump is connected, with the second check valve that the oil-out of second low-pressure oil pump is connected, the fuel rail of holding pressure that is connected with first check valve and second check valve, set up the fuel pressure sensor on the fuel rail of holding pressure and the pressure regulating valve who is connected with the oil-out of fuel rail of holding pressure, first low-pressure oil pump, second low-pressure oil pump, first check valve, second check valve and pressure regulating valve set up inside the box.

The first low-pressure oil pump and the second low-pressure oil pump are arranged in the box body side by side, and the first low-pressure oil pump and the second low-pressure oil pump are located on the same side of the fuel oil pressure accumulation oil rail.

The first low-pressure oil pump, the second low-pressure oil pump and the pressure regulating valve are positioned on the same side of the fuel oil pressure accumulation oil rail, and the first low-pressure oil pump is positioned between the second low-pressure oil pump and the pressure regulating valve.

When the first low-pressure oil pump works and the second low-pressure oil pump does not work, at the moment, the detection result of the fuel pressure sensor correspondingly represents the system fuel pressure when the first low-pressure oil pump is damaged.

The oil pump assembly suitable for the piston type aircraft engine further comprises a shock pad which is arranged inside the box body and is made of soft materials, and the shock pad is located between the first low-pressure oil pump and the box body, and between the second low-pressure oil pump and the box body.

The shock pad is made of rubber materials.

And the oil inlets of the first low-pressure oil pump and the second low-pressure oil pump are provided with pressure relief valves.

The box body comprises a lower shell and an upper cover connected with the lower shell.

The invention also provides a piston type aero-engine which comprises the oil pump assembly.

The invention is suitable for the oil pump assembly of the piston type aircraft engine, can reduce the complexity of the system and has high integration level.

Drawings

The description includes the following figures, the contents shown are respectively:

FIG. 1 is an exploded schematic view of an oil pump assembly suitable for use in a piston aircraft engine in accordance with the present invention;

FIG. 2 is a schematic view of the fuel flow direction of an oil pump assembly suitable for use in a piston aircraft engine according to the present invention;

labeled as: 1. an upper cover; 2. a fuel pressure sensor; 3. a fuel rail for accumulating fuel; 4. plugging an oil rail; 5. a pressure regulating valve; 6. a first low-pressure oil pump; 7. a shock pad; 8. a lower case; 9. a pressure relief valve; 10. an oil pump clamp; 11. a second low-pressure oil pump; 12. a first harness insert; 13. a first check valve; 14. a second one-way valve; 15. a first oil inlet pipe; 16. a second oil inlet pipe; 17. an oil outlet pipe; 18. a second harness insert; 19. and an oil return port.

Detailed Description

The following detailed description of the embodiments of the present invention will be given with reference to the accompanying drawings for a purpose of helping those skilled in the art to more fully, accurately and deeply understand the concept and technical solution of the present invention and to facilitate its implementation.

It should be noted that, in the following embodiments, the "first" and "second" do not represent an absolute distinction relationship in structure and/or function, nor represent a sequential execution order, but merely for convenience of description.

As shown in fig. 1 and 2, the present invention provides an oil pump assembly suitable for a piston type aircraft engine, including a first low-pressure oil pump 6, a second low-pressure oil pump 11, a tank, a first check valve 13 connected to an oil outlet of the first low-pressure oil pump 6, a second check valve 14 connected to an oil outlet of the second low-pressure oil pump 11, a fuel pressure accumulating rail 3 connected to the first check valve 13 and the second check valve 14, a fuel pressure sensor 2 disposed on the fuel pressure accumulating rail 3, a pressure regulating valve 5 connected to an oil outlet of the fuel pressure accumulating rail 3, and an oil outlet pipe 17 connected to the pressure regulating valve 5, wherein the first low-pressure oil pump 6, the second low-pressure oil pump 11, the first check valve 13, the second check valve 14, and the pressure regulating valve 5 are disposed inside the tank.

Specifically, as shown in fig. 1 and 2, the casing has a hollow rectangular structure, the first low-pressure oil pump 6 and the second low-pressure oil pump 11 are arranged side by side in the casing, and the first low-pressure oil pump 6 and the second low-pressure oil pump 11 are located on the same side of the fuel rail 3. The length directions of the first low-pressure oil pump 6 and the second low-pressure oil pump 11 are parallel to the length direction of the box body, the first low-pressure oil pump 6 and the second low-pressure oil pump 11 are positioned on the same straight line parallel to the width direction of the box body, the length direction of the fuel pressure accumulating oil rail 3 is parallel to the width direction of the box body, the fuel pressure accumulating oil rail 3 is positioned at one end of the box body in the length direction, and the fuel pressure accumulating oil rail 3 is fixedly connected with the box body. First low-pressure oil pump 6, second low-pressure oil pump 11 and pressure regulating valve 5 are located same one side of fuel rail 3, and first low-pressure oil pump 6 is located between second low-pressure oil pump 11 and pressure regulating valve 5, and first low-pressure oil pump 6, second low-pressure oil pump 11 and pressure regulating valve 5 are in the collinear with the width direction of box parallels, and pressure regulating valve 5 and box fixed connection.

As shown in fig. 1 and 2, the piston type aircraft engine is a diesel engine, the oil outlet pipe 17 is used for guiding the fuel from the pressure regulating valve 5 to a fuel fine filter of the piston type aircraft engine, the fuel filtered by the fuel fine filter flows to a high-pressure oil pump of the piston type aircraft engine, and the high-pressure oil pump supplies oil to a fuel rail of the piston type aircraft engine. One end of the oil outlet pipe 17 is connected with an oil outlet of the pressure regulating valve 5, the other end of the oil outlet pipe 17 penetrates through the side wall of the box body and then extends out towards the outer side of the box body, an oil inlet of the pressure regulating valve 5 is connected with an oil outlet of the fuel pressure accumulating oil rail 3, and the length direction of the oil outlet pipe 17 is parallel to the length direction of the box body.

As shown in fig. 1 and 2, an oil inlet of the first low-pressure oil pump 6 is connected to a first oil inlet pipe 15, an oil inlet of the second low-pressure oil pump 11 is connected to a second oil inlet pipe 16, the first oil inlet pipe 15 and the second oil inlet pipe 16 are located outside the tank body, the first oil inlet pipe 15 and the second oil inlet pipe 16 are arranged side by side, the first oil inlet pipe 15, the second oil inlet pipe 16 and the oil outlet pipe 17 are located on the same straight line parallel to the width direction of the tank body, and the first oil inlet pipe 15 and the second oil inlet pipe 16 are connected to the fuel tank. An oil outlet of the first low-pressure oil pump 6 is connected with an oil inlet of a first one-way valve 13, an oil outlet of the first one-way valve 13 is connected with an oil inlet of the fuel pressure accumulation oil rail 3, an oil outlet of the second low-pressure oil pump 11 is connected with an oil inlet of a second one-way valve 14, and an oil outlet of the second one-way valve 14 is connected with another oil inlet of the fuel pressure accumulation oil rail 3. The first check valve 13 allows fuel to flow only from the first low-pressure fuel pump 6 to the fuel rail 3, and fuel in the fuel rail 3 cannot flow back to the first low-pressure fuel pump 6 through the first check valve 13, and similarly, the second check valve 14 allows fuel to flow only from the second low-pressure fuel pump 11 to the fuel rail 3, and fuel in the fuel rail 3 cannot flow back to the second low-pressure fuel pump 11 through the second check valve 14. Therefore, the two one-way valves are arranged to prevent the fuel pumped by the two low-pressure oil pumps from flowing back to the low-pressure oil pump, the fuel pumped by the first low-pressure oil pump 6 and the fuel pumped by the second low-pressure oil pump 11 are converged in the fuel pressure accumulation rail 3, and the fuel pressure accumulation rail 3 is used for performing pressure stabilization treatment on the fuel output by the first low-pressure oil pump 6 and the second low-pressure oil pump 11, so that certain fuel pressure fluctuation is eliminated, and the fuel pressure output by the fuel pressure accumulation rail is more stable.

As shown in fig. 1 and 2, the first low-pressure oil pump 6 and the second low-pressure oil pump 11 are both electric oil pumps, the first low-pressure oil pump 6 and the second low-pressure oil pump 11 are controlled by a controller, the first low-pressure oil pump 6 and the second low-pressure oil pump 11 are controlled by the controller to be in suction power supply through a relay, the power supply roller pump assemblies of the first low-pressure oil pump 6 and the second low-pressure oil pump 11 rotate to generate vacuum degree at an oil pump oil suction port, and fuel is sucked out of a fuel tank by the oil pumps. The fuel pressure sensor 2 is used for detecting the fuel pressure in the fuel pressure accumulation fuel rail 3, and the output voltage value of the first low-pressure oil pump 6 and the second low-pressure oil pump 11 during normal fuel supply is calibrated through the fuel pressure sensor 2 to represent the fuel pressure of the system during normal work; when the first low-pressure oil pump 6 works and the second low-pressure oil pump 11 does not work, the detection result of the fuel pressure sensor 2 correspondingly represents the system fuel pressure when the first low-pressure oil pump 6 is damaged; when the second low-pressure oil pump 11 is operated and the first low-pressure oil pump 6 is not operated, the detection result of the fuel pressure sensor 2 at this time corresponds to the system fuel pressure when the second low-pressure oil pump 11 is damaged. The fuel pressure sensor 2 is electrically connected with the controller, when the pumping pressures of the first low-pressure oil pump 6 and the second low-pressure oil pump 11 are too high or too low, voltage signals can be output through the fuel pressure sensor 2, the signals are processed by the controller analog-to-digital conversion module (analog signals are converted into digital signals), and the controller records fault code information and judges whether alarm information is sent out or not through the definition of a control strategy.

As shown in fig. 1 and 2, the oil pump assembly suitable for the piston-type aircraft engine further includes a shock pad 7 which is arranged inside the tank and is made of soft material, and the shock pad 7 is located between the first low-pressure oil pump 6 and the second low-pressure oil pump 11 and the tank. The shock absorbing pad 7 plays a role in shock absorption, and can give sufficient protection and shock absorption to the first low-pressure oil pump 6 and the second low-pressure oil pump 11 during the flight of the aircraft.

Preferably, the shock pad 7 is made of rubber, the shock pad 7 is sandwiched between the first low-pressure oil pump 6 and the inner wall surface of the casing, the shock pad 7 is also sandwiched between the second low-pressure oil pump 11 and the inner wall surface of the casing, and the length direction of the shock pad 7 is parallel to the length direction of the casing.

The pressure regulating valve 5 is used for enabling the pressure of fuel flowing to the oil outlet pipe 17 to be within a set range, the fuel is finally output through the regulation of the pressure regulating valve 5, the flow of a fuel medium is regulated and the pressure of the fuel is controlled by the pressure regulating valve 5 through controlling the opening degree of an opening and closing piece in a valve body, the pressure of the fuel output by the whole system can be stabilized within a certain range, and the oil inlet pressure requirement of a high-pressure fuel system is met.

As shown in fig. 1 and fig. 2, preferably, the first low-pressure oil pump 6 and the second low-pressure oil pump 11 are provided with a pressure relief valve 9 at oil inlets thereof, and the pressure relief valve 9 is connected to the fuel tank through an oil return pipe, so that when the pressure regulating valve 5 is abnormal or the oil pressure is abnormally increased, the first low-pressure oil pump 6 and the second low-pressure oil pump 11 continuously supply oil and the increased oil pressure can be returned through the pressure relief valve 9, thereby ensuring the safety of the whole system.

As shown in fig. 1 and 2, the box includes inferior valve 8 and the upper cover 1 of being connected with inferior valve 8, upper cover 1 and inferior valve 8 fixed connection, inferior valve 8 is inside hollow rectangle shell structure, first low-pressure oil pump 6, second low-pressure oil pump 11, fuel pressure accumulation oil rail 3 and pressure regulating valve 5 are fixed to be set up in inferior valve 8, upper cover 1 seals the opening of inferior valve 8, shock pad 7 presss from both sides between the internal face of first low-pressure oil pump 6 and second low-pressure oil pump 11 and inferior valve 8, first low-pressure oil pump 6 and second low-pressure oil pump 11 pass through the oil pump clamp to be fixed in the cavity in inferior valve 8.

As shown in fig. 2, a first oil inlet pipe 15 and a second oil inlet pipe 16 are connected with a fuel tank, a first wire harness plug-in 12, a second wire harness plug-in 18 and a wire harness plug-in of a fuel pressure sensor 2 are reliably connected with a wire harness assembly corresponding to a matching plug-in connector, an oil return of a pressure regulating valve 5 is connected with the fuel tank, an oil outlet pipe 17 is connected with a fuel fine filter, a controller controls the relay suction of a first low pressure oil pump 6 and a second low pressure oil pump 11, the first low pressure oil pump 6 and the second low pressure oil pump 11 are electrified to start working, fuel pumped by the first low pressure oil pump 6 and the second low pressure oil pump 11 respectively flows to a fuel pressure accumulation oil rail 3 through a first check valve 13 and a second check valve 14, the fuel sequentially enters a high pressure oil pump through the pressure regulating valve 5, the oil outlet pipe 17, the fuel fine filter and the fuel rail, the controller is in closed-loop control with the, and PID (proportion integration differentiation) adjustment is carried out to correct the deviation, so that theoretically, the opening of the fuel metering valve can be adjusted by the closed loop of the controller according to the fuel delivery quantity of the double low-pressure oil pumps working simultaneously, the actual rail pressure of the fuel rail of the diesel engine reaches the target rail pressure, and the rail pressure of the fuel rail is kept in a stable state.

When one of the first low-pressure oil pump 6 and the second low-pressure oil pump 11 does not work, the oil output of the other oil pump which works normally can be regulated to be stable high-pressure system required oil pressure through the pressure regulating valve 5, the current of the fuel metering valve of the high-pressure oil pump is regulated through the difference of reduced flow by combining a controller with a rail pressure sensor signal closed loop PID (proportion integration differentiation), the opening of the fuel metering valve is further controlled and regulated, the quantitative fuel is controlled to enter a high-pressure oil pump plunger cavity for pressurization, the actual rail pressure of the diesel engine oil rail is also realized to achieve the target rail pressure, and the rail pressure of the diesel engine oil rail is kept in a stable state. When the fuel pressure in the fuel rail is kept stable, the controller reasonably controls the power-on time and the fuel injection timing of the electromagnetic valve of the fuel injector, so that the performance index of the engine is not influenced by the abnormality of a single pump of a low-pressure fuel system.

Meanwhile, under the condition that the system is abnormal, the fuel pressure sensor 2 arranged on the fuel pressure accumulation fuel rail 3 outputs a voltage signal inconsistent with the calibrated normal condition, and by comparing the calibration characteristic curve of the output voltage of the fuel pressure sensor 2 and the fuel pressure, the controller can process and judge whether the system oil pressure is in the abnormal condition at the moment, record a fault code and judge whether to alarm, prompt an operator of the abnormal condition and carry out maintenance or replacement in time.

The fuel pressure sensor 2 collects the oil pressure in the fuel pressure accumulation oil rail 3 and transmits a signal to the controller, when the controller judges that the oil pressure in the fuel pressure accumulation oil rail 3 is not in a set range according to the signal sent by the fuel pressure sensor 2, the controller judges that the oil pump assembly at the moment is in an abnormal condition, the oil pump assembly is in a failure mode, the controller sends an alarm signal to the alarm device, and the alarm device sends a failure alarm to prompt the check of failure. The alarm device is arranged in the aircraft cockpit, and can be a fault alarm lamp or a buzzer

Therefore, the control strategy of the oil pump assembly of the present invention can ensure that when the first low-pressure oil pump 6 and the second low-pressure oil pump 11 are controlled simultaneously, the output oil quantity of the oil pump assembly can meet the fuel quantity demand of the engine, and when any one of the first low-pressure oil pump 6 and the second low-pressure oil pump 11 is abnormal, the output oil quantity of the remaining one of the low-pressure oil pumps should also meet the fuel quantity demand of the engine. Meanwhile, the controller can record and select whether to alarm the abnormal state of the oil pump through the sensor signal so as to facilitate the inspection and further processing of an operator.

The invention also provides a piston type aero-engine which comprises the oil pump assembly with the structure. The specific structure of the oil pump assembly can refer to fig. 1 and 2, and is not described herein. Since the piston-type aircraft engine according to the invention comprises the oil pump assembly of the embodiment described above, it has all the advantages of the oil pump assembly described above.

The oil pump assembly with the structure has the following advantages:

1) the maintenance is better, the efficiency of maintenance and fault elimination is high, the component module is directly replaced when an abnormity occurs, and the sub-components do not need to be checked one by one;

2) the product quality control is easier, and the matching application and quality detection of a host factory and a terminal client are more convenient by defining the modularized product delivery standard than defining various sub-component standards;

3) the oil pump assembly is developed to be mature, and can be directly transplanted to be applied to different application fields after reliability verification;

4) the upgrading performance is better, the oil pump assembly module can be upgraded in the aspects of performance or reliability by replacing sub-parts, and the requirements of different application fields can be met;

5) the safety is higher, a feasible scheme is provided for improving the safety of a low-pressure oil supply system of the common rail diesel engine, the oil pump assembly adopts a double low-pressure oil pump redundancy design, and after one low-pressure oil pump stops working, the other low-pressure oil pump can still ensure the normal working of the common rail engine; the fuel pressure sensor can detect and alarm fault signals;

6) the consistency of the product is easier to control, the sub-parts such as a low-pressure oil pump, an oil pipe and a pressure regulating valve are relatively fixed in the module, so that the output characteristic of an oil pump assembly and the consistency of the product are easier to control compared with the distributed sub-parts, and the pressure regulating valve designed in the oil pump assembly can ensure that the oil pump assembly outputs stable fuel pressure, the fuel parameter output to the inlet of a high-pressure fuel system of an engine by the oil pump assembly is more controllable, and the matching calibration of the high-pressure fuel system and the low-pressure fuel system is more excellent;

7) the protective performance is higher, the key parts of the low-pressure fuel system are protected through the shell and the shock pad to form an oil pump assembly, and the key parts can be effectively prevented from being influenced by corrosion, vibration and electromagnetic interference;

8) the oil pump assembly has the capability of maintaining work in the abnormal state of system oil pressure, when the oil pump assembly is internally provided with the pressure release valve, the abnormal rise of the system oil pressure can be ensured, the overhigh fuel oil pressure can be released through the pressure release valve and kept to a relatively safe and stable low-pressure system oil pressure, a fuel oil pressure sensor can detect and alarm fault signals under the oil pressure, and meanwhile, the engine can also be maintained to run in the limit state and is detected and maintained to a maintenance place.

The invention is described above with reference to the accompanying drawings. It is to be understood that the specific implementations of the invention are not limited in this respect. Various insubstantial improvements are made by adopting the method conception and the technical scheme of the invention; the present invention is not limited to the above embodiments, and can be modified in various ways.

Claims (9)

1. Oil pump assembly suitable for piston aeroengine, including first low-pressure oil pump and second low-pressure oil pump, its characterized in that: the oil-saving device comprises a first low-pressure oil pump, a second low-pressure oil pump, a first check valve, a second check valve, a fuel pressure accumulation oil rail, a fuel pressure sensor and a pressure regulating valve, wherein the first check valve is connected with an oil outlet of the first low-pressure oil pump, the second check valve is connected with an oil outlet of the second low-pressure oil pump, the fuel pressure accumulation oil rail is connected with the first check valve and the second check valve, the fuel pressure sensor is arranged on the fuel pressure accumulation oil rail, the pressure regulating valve is connected with the oil outlet of the fuel pressure accumulation oil rail, and the first low-pressure oil pump, the second low-pressure.

2. Oil pump assembly suitable for use in a piston-type aeroengine, according to claim 1, characterized in that: the first low-pressure oil pump and the second low-pressure oil pump are arranged in the box body side by side, and the first low-pressure oil pump and the second low-pressure oil pump are located on the same side of the fuel oil pressure accumulation oil rail.

3. Oil pump assembly suitable for use in a piston-type aeroengine, according to claim 2, characterized in that: the first low-pressure oil pump, the second low-pressure oil pump and the pressure regulating valve are positioned on the same side of the fuel oil pressure accumulation oil rail, and the first low-pressure oil pump is positioned between the second low-pressure oil pump and the pressure regulating valve.

4. Oil pump assembly suitable for use in a piston-type aircraft engine according to any one of claims 1 to 3, characterized in that: when the first low-pressure oil pump works and the second low-pressure oil pump does not work, at the moment, the detection result of the fuel pressure sensor correspondingly represents the system fuel pressure when the first low-pressure oil pump is damaged.

5. Oil pump assembly suitable for use in a piston-type aircraft engine according to any one of claims 1 to 4, characterized in that: still including set up in the inside shock pad that just adopts soft materials to make of box, the shock pad is located between first low-pressure oil pump and second low-pressure oil pump and the box.

6. Oil pump assembly suitable for use in a piston-type aeroengine according to claim 5, characterized in that: the shock pad is made of rubber materials.

7. Oil pump assembly suitable for use in a piston-type aircraft engine according to any one of claims 1 to 6, characterized in that: and the oil inlets of the first low-pressure oil pump and the second low-pressure oil pump are provided with pressure relief valves.

8. Oil pump assembly suitable for use in a piston-type aircraft engine according to any one of claims 1 to 7, characterized in that: the box body comprises a lower shell and an upper cover connected with the lower shell.

9. Piston aeroengine, its characterized in that: comprising an oil pump assembly according to any one of claims 1 to 8.

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